Antenna adapter pad

Abstract

Systems and methods are described for replacing one or more antennas of an aircraft without requiring removal of the mounting structure of the avionics antenna that is attached to a fuselage of the aircraft. An antenna adapter pad can be removably secured to the mounting structure, such that different antenna adapter pads can be secured to the mounting structure over time to allow replacement and / or repair of antenna electronics attached to each of the antenna adapter pads without requiring removal of the mounting structure itself.

Description

ANTENNA ADAPTER PAD

[0001] This application claims priority to U.S. provisional patent application having serial number 63 / 592,774, filed on October 24, 2023. This and all other referenced extrinsic materials are incorporated herein by reference in their entirety. Where a definition or use of a term in a reference that is incorporated by reference is inconsistent or contrary to the definition of that term provided herein, the definition of that term provided herein is deemed to be controlling.Field of the Invention

[0002] The field of the invention is avionic antennas, and more specifically, a structure for removably mounting one or more antennas to an aircraft.Background

[0003] The following description includes information that may be useful in understanding the present invention. It is not an admission that any of the information provided herein is prior art or relevant to the presently claimed invention, or that any publication specifically or implicitly referenced is prior art.

[0004] Provision of aircraft with the ability to link to satellite communication networks necessarily entails the use of one or more avionic antennas, which are generally external to an aircraft. Typically, when a new satellite communications antenna is to be installed on an aircraft, the new installation requires a completely new certification in a certified aircraft crown mounting installation.

[0005] The certification process is generally a lengthy and expensive process. Because the complete assembly of the avionics antenna is replaced including the structure mounting to a fuselage of the aircraft, the process generally requires a full aircraft certification to be conducted when the newer technology antenna (and its support structure) is installed.

[0006] While airlines may desire to upgrade their satellite communications equipment, the significant time and cost involved to do so and to complete the certification process makes such upgrades less desirable or prohibitive.

[0007] Thus, there is still a need for improved apparatus and processes for replacing satellite communication antenna on aircraft without the need for full certification of the newly installed antenna.Summary of The Invention

[0008] The inventive subject matter provides apparatus, systems, and methods for a mounting structure for an avionics antenna that advantageously allows for different antenna electronics to be secured and used by the aircraft without requiring full replacement and certification of a new mounting structure compatible with the new antenna electronics. Otherwise, the entire antenna mounting structure would require replacement every time the antenna electronics are changed.

[0009] In some embodiments, antenna mounts for an avionics antenna for an aircraft are contemplated, which comprise an aircraft mounting structure configured to be attached to an aircraft. Contrary to prior art structure, the antenna mount comprises an antenna adapter pad that is removably attachable to the aircraft mounting structure. The antenna adapter pad is configured to receive and secure first antenna electronics, such that the first antenna electronics can then be secured to the aircraft mounting structure via the antenna adapter pad.

[0010] To replace the first antenna electronics with different antenna electronics, the antenna adapter pad can be detached from the aircraft mounting structure and a second antenna adapter pad can be attached to the aircraft mounting structure in place of the antenna adapter pad and first antenna electronics. It is contemplated that the second antenna adapter pad comprises second antenna electronics that are different from the first antenna electronics.

[0011] It is further contemplated that one or both of the antenna adapter pad and the second antenna adapter pad can comprise one or more flat surfaces to which antenna electronics can be secured. The flat surfaces can advantageously also be utilized as a heat sink to expel heat away from the antenna electronics. One or both of the antenna adapter pad and the second antenna adapter pad can further comprise a set of fins disposed on a lower surface of the antenna adapter pad (or second antenna adapter pad) opposite a surface where the antenna electronics attaches to the antenna adapter pad (or second antenna adapter pad).

[0012] In other embodiments, methods of replacing antenna electronics of an avionics antenna mounted to an aircraft are contemplated. It is contemplated that the avionics antenna comprises a mounting structure attached to the aircraft. A first antenna adapter pad comprising first antenna electronics may be attached to the mounting structure. When desired, the first antenna adapter pad can be removed from the mounting structure attached to the aircraft, thereby also removing the first antenna electronics.

[0013] A second antenna adapter pad can be secured to the mounting structure, which thereby allows the second antenna electronics coupled to the second antenna adapter pad to also be secured to the mounting structure and therefore the aircraft. The replacement of the first antenna electronics with the second antenna electronics is preferably accomplished without requiring removal and replacement of the mounting structure attached to the aircraft. More importantly, by not requiring removal and replacement of the mounting structure itself, the second antenna electronics can preferably be installed on the aircraft without necessitating a full recertification process.

[0014] Various objects, features, aspects and advantages of the inventive subject matter will become more apparent from the following detailed description of preferred embodiments, along with the accompanying drawing figures in which like numerals represent like components.Brief Description of The Drawings

[0015] Figure 1 illustrates a perspective view of one embodiment of an avionics antenna.

[0016] Figure 2 illustrates a top perspective, exploded view of the avionics antenna of Figure 1.

[0017] Figure 3 illustrates a bottom perspective, exploded view of the avionics antenna of Figure 1.

[0018] Figures 4-5 illustrates top and bottom perspective views, respectively, of the antenna adapter pad shown in Figure 1.

[0019] Figure 6 illustrates one embodiment of a method of replacing antenna electronics of an avionics antenna mounted to an aircraft.Detailed Description

[0020] The following discussion provides many example embodiments of the inventive subject matter. Although each embodiment represents a single combination of inventive elements, the inventive subject matter is considered to include all possible combinations of the disclosed elements. Thus, if one embodiment comprises elements A, B, and C, and a second embodiment comprises elements B and D, then the inventive subject matter is also considered to include other remaining combinations of A, B, C, or D, even if not explicitly disclosed.

[0021] The inventive subject matter provides apparatus, systems, and methods for an antenna adapter pad, which advantageously can be used to isolate the antenna from the aircraft mounting points. This novel concept allows the existing crown assembly including the mounting structure attached to the aircraft to be modified with minimal certification effort and expense. The use of an antenna adapter pad, such as those described herein, advantageously allows the aircraft satellite communication antennas to be updated with much less cost and time that the current technique of wholesale removal and replacement.

[0022] An added benefit to the use of the antenna adapter pad is an improved management of heat generated by high-powered antenna electronics contained in the radome, as discussed further below.

[0023] Figures 1-5 illustrates one embodiment of an antenna mount for an avionics antenna 100 that can preferably be mounted to an aircraft. The antenna mount preferably comprises an aircraft mounting structure 102 configured to be attached to a fuselage of the aircraft. It is contemplated that the aircraft mounting structure 102 may be permanently affixed to the aircraft in some embodiments.

[0024] An antenna adapter pad 104 can comprise first antenna electronics 108. Preferably, the antenna adapter pad 104 is removably attached to the aircraft mounting structure 102, such that the antenna adapter pad 104 and first antenna electronics 108 can be removed from the aircraft without requiring removal or replacement of the aircraft mounting structure 102.

[0025] In addition to providing mechanical adaptation between different antenna mount points and the fixed aircraft attachment, and as best shown in Figures 2-5, it is further contemplatedthat the antenna adapter pad 104 comprises one or more flat surfaces to which the first antenna electronics 108 is secured. The flat surfaces can help with thermal management and preferably act as a heat sink to thereby distribute heat produced by the first antenna electronics 108 evenly and conducting heat away from the first antenna electronics 108 to the aircraft mounting structure 102, for example. To further aid heat dissipation, the antenna adapter pad 104 may comprise a set of fins 110 disposed on a lower surface 112 of the antenna adapter pad 104 opposite a surface where the first antenna electronics 108 attaches to the antenna adapter pad 104

[0026] If additional heat dissipation is required, it is contemplated that the antenna adapter pad 104 could comprise additional fins and / or heat pipes to move heat away from the antenna electronics 108.

[0027] As shown in Figures 1-3, the avionics antenna 100 can comprise a radome 106 configured to attach to the aircraft mounting structure 102 and thereby encapsulate the first antenna electronics 108. The radome 106 thereby acts as a cover for the antenna electronics 108 to and provide an aerodynamic cover that protect the electronics 108 against the elements outside the aircraft.

[0028] Critically to replace the first antenna electronics 108 with second antenna electronics that are different from the first antenna electronics 108, the antenna adapter pad 104 can be removed from the aircraft mounting structure 102 and a second antenna adapter pad can be coupled to the aircraft mounting structure 102 in its place. In such embodiments, the second antenna adapter pad comprises the second antenna electronics, which are unable to attach to the antenna adapter pad 108. In this manner, the second antenna adapter pad can replace the antenna adapter pad and allow the second antenna electronics to be secured to the aircraft mounting structure without requiring removal of the aircraft mounting structure 102 from the aircraft or need for a different radome 106.

[0029] Once the second adapter pad is secured to the aircraft mounting structure 102, the radome 106 can again be used to now encapsulate the second antenna electronics and protect them from the elements while providing an aerodynamic cover.

[0030] It is contemplated that the first antenna electronics and the second antenna electronics can comprise any commercially suitable electronics for use with communications from an aircraft. Such electronics may include, for example, phased array antennas and other suitable types of antennas. Discussions of various types and configurations of antenna electronics can be found in WIPO patent application publication number PCT / US23 / 75147, filed on September 26, 2023, WIPO patent application publication number PCT / US23 / 25396, filed on June 15, 2023, U.S. patent number 10,931,003, issued on February 23, 2021, and U.S. patent number 10,468,759, issued on November 5, 2019.

[0031] As discussed above, these and all other referenced extrinsic materials are incorporated herein by reference in their entirety. Where a definition or use of a term in a reference that is incorporated by reference is inconsistent or contrary to the definition of that term provided herein, the definition of that term provided herein is deemed to be controlling.

[0032] Thus, using the inventive subject matter discussed herein, when replacing the old first antenna electronics with a newer second antenna electronics, for example, only the antenna adapter pad 104 is replaced. The radome 106 and aircraft mounting structure 102 remain in place as initially certified.

[0033] This can be accomplished using the structure and components discussed above and because initial certification of the adapter pad 104 and avionics antenna 100 utilized a peak weight and a center of gravity range, which thereby allow for different antenna electronics to be used that meets those weight and center of gravity parameters, and those antenna electronics to be installed on the aircraft with much less certification effort than if a specific weight and center of gravity was certified.

[0034] Figure 6 illustrates one embodiment of a method 200 of replacing an antenna of an avionics antenna mounted to a fuselage of an aircraft. It is contemplated that the avionics antenna comprises a mounting structure attached to the aircraft and a radome configured to encapsulate antenna electronics of the avionics antenna.

[0035] In step 210, a first antenna adapter pad is removed or detached from the mounting structure that is attached to the aircraft. Preferably, first antenna electronics are attached to the first antenna adapter pad.

[0036] In step 220, a second antenna adapter pad is attached or otherwise secured to the mounting structure without requiring removal of the mounting structure attached to the aircraft. Preferably, second antenna electronics are attached to the second antenna adapter pad. In this manner, the first antenna electronics can be replaced with the second antenna electronics without needing to replace or recertify the entire avionics antenna. The second antenna adapter pad secures the second antenna electronics to the mounting structure attached to the aircraft.

[0037] In such embodiments, the second antenna electronics are preferably different than the first antenna electronics and unable to attach to the first antenna adapter pad.

[0038] As discussed above, one or both of the first antenna adapter pad and the second antenna adapter pad can compromise one or more flat surfaces to which the respective antenna electronics attach. The flat surface can act as a heat sink to distribute heat evenly from the antenna electronics. One or both of the first antenna adapter pad and the second antenna adapter pad can further comprise a set of fins disposed on a lower surface of the antenna adapter pad opposite a surface where the antenna electronics attaches to the antenna adapter pad.

[0039] As discussed above, the first antenna electronics and the second antenna electronics can comprise any commercially suitable electronics for use with communications from an aircraft including, for example, phased array antennas and other suitable types of antennas including those described in the referenced patent documents.

[0040] As used herein, and unless the context dictates otherwise, the term "coupled to" is intended to include both direct coupling (in which two elements that are coupled to each other contact each other) and indirect coupling (in which at least one additional element is located between the two elements). Therefore, the terms "coupled to" and "coupled with" are used synonymously.

[0041] Unless the context dictates the contrary, all ranges set forth herein should be interpreted as being inclusive of their endpoints and open-ended ranges should be interpreted to include onlycommercially practical values. Similarly, all lists of values should be considered as inclusive of intermediate values unless the context indicates the contrary.

[0042] As used in the description herein and throughout the claims that follow, the meaning of “a,” “an,” and “the” includes plural reference unless the context clearly dictates otherwise. Also, as used in the description herein, the meaning of “in” includes “in” and “on” unless the context clearly dictates otherwise.

[0043] The recitation of ranges of values herein is merely intended to serve as a shorthand method of referring individually to each separate value falling within the range. Unless otherwise indicated herein, each individual value with a range is incorporated into the specification as if it were individually recited herein. All methods described herein can be performed in any suitable order unless otherwise indicated herein or otherwise clearly contradicted by context. The use of any and all examples, or exemplary language (e.g. “such as”) provided with respect to certain embodiments herein is intended merely to better illuminate the invention and does not pose a limitation on the scope of the invention otherwise claimed. No language in the specification should be construed as indicating any non-claimed element essential to the practice of the invention.

[0044] Groupings of alternative elements or embodiments of the invention disclosed herein are not to be construed as limitations. Each group member can be referred to and claimed individually or in any combination with other members of the group or other elements found herein. One or more members of a group can be included in, or deleted from, a group for reasons of convenience and / or patentability. When any such inclusion or deletion occurs, the specification is herein deemed to contain the group as modified thus fulfilling the written description of all Markush groups used in the appended claims.

[0045] It should be apparent to those skilled in the art that many more modifications besides those already described are possible without departing from the inventive concepts herein. The inventive subject matter, therefore, is not to be restricted except in the spirit of the appended claims. Moreover, in interpreting both the specification and the claims, all terms should be interpreted in the broadest possible manner consistent with the context. In particular, the terms “comprises” and “comprising” should be interpreted as referring to elements, components, orsteps in a non-exclusive manner, indicating that the referenced elements, components, or steps may be present, or utilized, or combined with other elements, components, or steps that are not expressly referenced. Where the specification claims refers to at least one of something selected from the group consisting of A, B, C .... and N, the text should be interpreted as requiring only one element from the group, not A plus N, or B plus N, etc.

Claims

CLAIMSWhat is claimed is:

1. An antenna mount for an avionics antenna, comprising: an aircraft mounting structure configured to be attached to an aircraft; an antenna adapter pad removably attachable to the aircraft mounting structure, wherein the antenna adapter pad is configured to receive first antenna electronics; and wherein the antenna adapter pad comprises one or more flat surfaces to which the first antenna electronics can be secured.

2. The antenna mount of claim 1, comprising: a second antenna adapter pad configured to replace the antenna adapter pad and attach to the aircraft mounting structure; and wherein the second antenna adapter pad is configured to receive second antenna electronics that are unable to attach to the antenna adapter pad, such that the second antenna adapter pad can replace the antenna adapter pad and allow the second antenna electronics to be secured to the aircraft mounting structure.

3. The antenna mount of claim 2, wherein the antenna adapter pad is replaced with the second antenna adapter pad without requiring removal of the aircraft mounting structure from the aircraft.

4. The antenna mount of claim 2, wherein the second antenna electronics are different than the first antenna electronics.

5. The antenna mount of claim 1, wherein the antenna adapter pad comprises a set of fins disposed on a lower surface of the antenna adapter pad opposite a surface where the first antenna electronics attaches to the antenna adapter pad.

6. The antenna mount of claim 5, wherein the antenna adapter pad is configured to act as a heat sink for the first antenna electronics to dissipate heat from the first antenna electronics.

7. The antenna mount of claim 1, wherein the aircraft mounting structure is configured to be attached to a fuselage of the aircraft.

8. The antenna mount of claim 1, wherein the first antenna electronics comprise a phased array antenna.

9. The antenna mount of claim 1, further comprising: a radome configured to attach to the aircraft mounting structure and thereby encapsulate the first antenna electronics.

10. A method of replacing antenna electronics of an avionics antenna mounted to an aircraft, wherein the avionics antenna comprises a mounting structure attached to the aircraft, the method comprising: removing a first antenna adapter pad from the mounting structure attached to the aircraft, wherein first antenna electronics are attached to the first antenna adapter pad; and securing a second antenna adapter pad to the mounting structure, wherein second antenna electronics are attached to the second antenna adapter pad, thereby replacing the first antenna electronics with the second antenna electronics without requiring removal of the mounting structure attached to the aircraft.

11. The method of claim 10, wherein the second antenna electronics are different than the first antenna electronics.

12. The method of claim 11, wherein the second antenna electronics are unable to attach to the first antenna adapter pad.

13. The method of claim 10, wherein the second antenna adapter pad secures the second antenna electronics to the mounting structure attached to the aircraft.

14. The method of claim 10, wherein the first antenna adapter pad comprises a set of fins disposed on a lower surface of the first antenna adapter pad opposite a surface where the first antenna electronics attaches to the first antenna adapter pad.

15. The method of claim 14, wherein the first antenna adapter pad acts as a heat sink for the first antenna electronics to move heat away from the first antenna electronics.

16. The method of claim 10, wherein the aircraft mounting structure is attached to a fuselage of the aircraft.

17. The method of claim 10, wherein at least one of the first antenna electronics and the second antenna electronics comprises a phased array antenna.

18. The method of claim 10, wherein the avionics antenna comprises a radome configured to attach to the aircraft mounting structure.

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